A thorough experimental investigation of shock/shock interferences in high Mach number flows

Boldyrev, S. M.; Borovoy, V. Ya.; Chinilov, A. Yu.; Gusev, V. N.; Krutiy, Serge N; Struminskaya, I. V.; Yakovleva, L. V.; Délery, Jean; Chanetz, Bruno

doi:10.1016/s1270-9638(01)01094-x

Cited by 24 publications

(8 citation statements)

References 4 publications

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“…In this case, the supersonic jet embedded within the subsonic region is deflected upward sufficiently to graze the upper surface of the cylinder rather than impinge on the surface. This kind of interaction is classified as a type-IVa shock interaction [22]. The white square in Fig.…”

Section: A Quasi-steady Type-iv Shock Interactionsmentioning

confidence: 99%

Hypersonic Type-IV Shock/Shock Interactions on a Blunt Body with Forward-Facing Cavity

Xiao

Zhu

et al. 2017

Journal of Spacecraft and Rockets

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Section: A Quasi-steady Type-iv Shock Interactionsmentioning

confidence: 99%

Hypersonic Type-IV Shock/Shock Interactions on a Blunt Body with Forward-Facing Cavity

Xiao

Zhu

et al. 2017

Journal of Spacecraft and Rockets

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“…Studies (Wieting & Holden 1989; Boldyrev et al. 2001) show that as the Mach number increases, the detached shock moves closer to the wall and the heating load has an increasing trend. Therefore, it is crucial to explore the flow characteristics of VSBLE at a higher Mach number.…”

Section: Introductionmentioning

confidence: 99%

Modelling and shock control for a V-shaped blunt leading edge

et al. 2023

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Hypersonic flow on a V-shaped blunt leading edge (VSBLE) at Mach 12 is numerically investigated. A series of self-induced shock–shock interactions and shock wave/boundary layer interactions (SWBLIs) cause extremely high heat flux peaks on the crotch of the VSBLE. Based on these shock structures, a simplified model that divides the flow field into inviscid and viscous areas is constructed. This model can quickly solve the shock interactions and predict the heating/pressure peaks with high accuracy. Furthermore, a shock control bump (SCB) is placed on the SWBLI region to split the strong incident shock into a weaker multi-wave system. The mechanism study of the SCB shows that the inviscid effect significantly reduces the heating/pressure peaks, and the viscous effect suppresses the SWBLI-induced separation. Finally, a VSBLE with SCBs is numerically investigated. The heat flux peak is reduced by 66 % compared to that without the SCBs. The robustness of the SCB under various working conditions is also evaluated. This paper provides an idea for the simplified solution of complex shock interactions and extends the application of the SCB as a thermal protection device in hypersonic flow for the first time.

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“…When this jet touches the body, it produces high stagnation heating (Wieting & Holden 1989). When the incident shock wave takes a high position, the jet may bend upward without stagnating on the body and the jet is called type IVa or type VII shock interference (Yamamoto, Takasu & Nagatomo 1999;Boldyrev et al 2001;Windisch et al 2016).…”

Section: Introductionmentioning

confidence: 99%

Type IV shock interaction with a two-branch structured transonic jet

Bai

2022

J. Fluid Mech.

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Type IV shock interference has two triple points which produce two sliplines, forming a narrow jet that penetrates into the subsonic flow region behind the bow shock. Type IV shock interference in the case that the jet is supersonic has been extensively studied in the past. In this paper, type IV shock interference where the jet is transonic is studied. The transition condition from a supersonic to a transonic jet is identified and the influence of compression Mach waves, created inside the leading portion of the jet due to the pressure gradient outside the jet, on the transition and jet shape is analysed. It is found that these compression waves advance the transition from a supersonic to a transonic jet and make the flow inside the transonic jet have a two-branch structure: the lower branch is subsonic, the upper branch is supersonic and is composed of a combination of compressive and expansive waves. The mechanism by which the two-branch structure is produced is explained.

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A thorough experimental investigation of shock/shock interferences in high Mach number flows

Cited by 24 publications

References 4 publications

Hypersonic Type-IV Shock/Shock Interactions on a Blunt Body with Forward-Facing Cavity

Hypersonic Type-IV Shock/Shock Interactions on a Blunt Body with Forward-Facing Cavity

Modelling and shock control for a V-shaped blunt leading edge

Type IV shock interaction with a two-branch structured transonic jet

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